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Littérature scientifique sur le sujet « Aircraft cabins Noise Measurement »

Auteur : Grafiati

Publié le 4 juin 2021

Mis à jour le 1 février 2022

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Articles de revues sur le sujet "Aircraft cabins Noise Measurement"

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Hughes, Stanley T., et Jefferson Koonce. « Cabin Noise Levels in Single Engine General Aviation Aircraft ». Proceedings of the Human Factors Society Annual Meeting 30, n^o 14 (septembre 1986) : 1381–85. http://dx.doi.org/10.1177/154193128603001408.

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Sound level measurements were made on several of the most popular general aviation aircraft produced. Measurements were taken at various flight milestones such as; run up, taxi, climb, cruise power and descent. For each of the aircraft a time weighted mission sound level was obtained, using three different mission scenarios, varying only in flight time. For each of the three scenarios, and for all aircraft, the time weighted noise values obtained were an or exceeded the 85 dBA limit recommended by NIOSH. The results of this study indicate that a substantial percentage of general aviation pilots will show some loss of hearing due to the high noise levels present in their cabins. Recommendations are made for protection of occupants of general aviation aircraft.

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Kong, Qing Fu, Yu Liang Dai, Shi Jian Zhu et Jia Ming Wu. « Experimental Study on an Active Noise Control System for Turboprop Driven Aircraft ». Applied Mechanics and Materials 333-335 (juillet 2013) : 2142–45. http://dx.doi.org/10.4028/www.scientific.net/amm.333-335.2142.

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In order to find a solution to the control of low frequency noise in the cabin of turboprop driven aircraft, an experimental active noise control (ANC) system is introduced in the paper, which consists of vibroacoustic field analogue subsystem, acoustic field measurement subsystem and acoustic barrier exciter subsystem. Effects of both different spaces between the primary sound source and secondary sound source of the ANC system and different frequency noises on noise-reduction result are investigated based on the experimental platform. Results of the experiment show a significant potential of the ANC method for the control of low frequency noise in the cabin of turboprop driven aircraft.

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Joshi, Pankaj, Frank Khelfa, Hendrik Lehmkuhl, Patrick Cordes, Patrick Naujoks, Thorsten Scharowsky et Kay Kochan. « Design, development and testing of digital MEMS pressure sensor array for full-scale vibroacoustic measurements ». INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, n^o 2 (1 août 2021) : 4343–54. http://dx.doi.org/10.3397/in-2021-2671.

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This manuscript addresses design, development, and application of micro-electro-mechanical systems (MEMS) based digital pressure sensor array for vibroacoustic measurements. These vibroacoustic measurements were conducted on a A320 type single aisle aircraft demonstrator subjected to broadband as well as tonal excitations. Cabin noise levels were measured with both condenser microphones as well as digital MEMS pressure sensor array. The measured cabin noise shows strong qualitative as well as quantitative agreement between both type of measurement devises for full scale cabin noise measurements inside an aircraft demonstrator. The observed strong agreement is valid for both single wall (fuselage with thermal insulation) and double wall (fuselage with thermal insulation and trim panel) cabin noise measurements. Such strong agreement within 1.0 dB tolerance is significantly motivating for further development of reliable but low-cost MEMS based measurement devises and corresponding efficient data post-processing algorithms for full scale vibroacoustic measurements in general. Additionally, it is also demonstrated that the large number of MEMS based digital pressure sensors can be used in areas where the physical space constraints are high. This demonstration shows strong potential to derive additional vibroacoustic indicator for the development and the testing of future noise control solutions in a non-traditional way.

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Spehr, Carsten, Daniel Ernst et Hans-Georg Raumer. « MEMS microphone intensity array for cabin noise measurements ». INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, n^o 3 (1 août 2021) : 3023–34. http://dx.doi.org/10.3397/in-2021-2288.

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Aircraft cabin noise measurements in flight are used toto quantify the noise level, and to identify the entry point of acoustic energy into the cabin. Sound intensity probes are the state-of-the-art measurement technique for this task. During measurements, additional sound absorbing material is used to ease the rather harsh acoustic measurement environment inside the cabin. In order to decrease the expensive in-flight measurement time, an intensity array approach was chosen. This intensity probe consists of 512 MEMS-Microphones. Depending on the frequency, these microphones can be combined as an array of hundreds of 3D- intensity probes. The acoustic velocity is estimated using a high order 3D finite difference stencil. At low frequencies, a larger spacing is used to reduce the requirement of accurate phase match of the microphone sensors. Measurements were conducted in the ground-based Dornier 728 cabin noise simulation as well as in-flight.

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PAČAIOVÁ, Hana, Marianna TOMAŠKOVÁ, Michaela BALÁŽIKOVÁ et Jozef KRAJŇÁK. « Analysis of air-traffic threats ». Scientific Journal of Silesian University of Technology. Series Transport 110 (1 mars 2021) : 143–55. http://dx.doi.org/10.20858/sjsutst.2021.110.12.

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Globally, air transport has seen a greater increase in recent years. This manuscript is divided into three parts for analysing the negative effects of aviation. The first part is focused on the identification of sources of aircraft noise. While the second part of this article describes the basic principles of the construction and operation of an aircraft jet engine concerning the gaseous emissions produced by such an engine (Third part missing?). The main benefit of this article is the evaluation of the reliability of the human factor because the human factor is an integral part of technical systems and processes. Reliability assessment was performed using the TESEO method. The ergonomic parameter, that is, the cabin noise, was quantified in the given method. The measurement was performed on two types of aircraft, namely in the cabin of a transport jet aircraft and in the cabin of asmall transport aircraft equipped with turboprop engines.

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Schüür, Jens, Lukas Oppermann, Achim Enders, Rafael R. Nunes et Carl-Henrik Oertel. « Emission analysis of large number of various passenger electronic devices in aircraft ». Advances in Radio Science 14 (28 septembre 2016) : 129–37. http://dx.doi.org/10.5194/ars-14-129-2016.

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Abstract. The ever increasing use of PEDs (passenger or portable electronic devices) has put pressure on the aircraft industry as well as operators and administrations to reevaluate established restrictions in PED-use on airplanes in the last years. Any electronic device could cause electromagnetic interference to the electronics of the airplane, especially interference at receiving antennas of sensitive wireless navigation and communication (NAV/COM) systems. This paper presents a measurement campaign in an Airbus A320. 69 test passengers were asked to actively use a combination of about 150 electronic devices including many attached cables, preferentially with a high data load on their buses, to provoke maximal emissions. These emissions were analysed within the cabin as well as at the inputs of aircraft receiving antennas outside of the fuselage. The emissions of the electronic devices as well as the background noise are time-variant, so just comparing only one reference and one transmission measurement is not sufficient. Repeated measurements of both cases lead to a more reliable first analysis. Additional measurements of the absolute received power at the antennas of the airplane allow a good estimation of the real interference potential to aircraft NAV/COM systems. Although there were many measured emissions within the cabin, there were no disturbance signals detectable at the aircraft antennas.

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Zettel, Sebastian, René Winter, Marco Norambuena, Marc Böswald, Martin Richter et Gregor Tanner. « Finite element method and dynamical energy analysis in vibro-acoustics - A comparative study ». INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, n^o 5 (1 août 2021) : 1712–22. http://dx.doi.org/10.3397/in-2021-1906.

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Future aircraft concepts utilizing innovative lightweight structures and novel propulsion concepts are a necessity for long term sustainable air travel. These concepts pose new challenges for the vibro-acoustic assessment of cabin structures and the associated noise impact on passengers. Finite Element (FE) models derived from aircraft pre-design data are not optimized for use in acoustic analyses, i.e. the mesh is too coarse to provide meaningful results while setting up Statistical Energy Analysis models for this specific purpose is adding another time-consuming step. A possible alternative, Discrete Energy Analysis (DEA), is evaluated. This method allows to calculate the acoustic behavior of thin-walled structures in higher frequency ranges simply using existing FE meshes. In this paper an experimental lightweight aluminum structure and its respective FE model is investigated for a frequency range up to 5000 Hz. A comparison in terms of vibrational energy between DEA, FE and measurement results are presented. Finally, a lower-bound frequency range is identified in which DEA and FEM correlate and thus allow a substitution for further simulations at higher frequencies.

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Ross, Colin F. « Active noise control in aircraft cabins ». Journal of the Acoustical Society of America 105, n^o 2 (février 1999) : 1243. http://dx.doi.org/10.1121/1.425969.

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Kloss, Corinna, Vicheith Tan, J. Brian Leen, Garrett L. Madsen, Aaron Gardner, Xu Du, Thomas Kulessa et al. « Airborne Mid-Infrared Cavity enhanced Absorption spectrometer (AMICA) ». Atmospheric Measurement Techniques 14, n^o 8 (2 août 2021) : 5271–97. http://dx.doi.org/10.5194/amt-14-5271-2021.

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Abstract. We describe the Airborne Mid-Infrared Cavity enhanced Absorption spectrometer (AMICA) designed to measure trace gases in situ on research aircraft using Off-Axis Integrated Cavity Output Spectroscopy (OA-ICOS). AMICA contains two largely independent and exchangeable OA-ICOS arrangements, allowing for the simultaneous measurement of multiple substances in different infrared wavelength windows tailored to scientific questions related to a particular flight mission. Three OA-ICOS setups have been implemented with the aim to measure OCS, CO2, CO, and H2O at 2050 cm−1; O3, NH3, and CO2 at 1034 cm−1; and HCN, C2H2, and N2O at 3331 cm−1. The 2050 cm−1 setup has been characterized in the laboratory and successfully used for atmospheric measurements during two campaigns with the research aircraft M55 Geophysica and one with the German HALO (High Altitude and Long Range Research Aircraft). For OCS and CO, data for scientific use have been produced with 5 % accuracy (15 % for CO below 60 ppb, due to additional uncertainties introduced by dilution of the standard) at typical atmospheric mixing ratios and laboratory-measured 1σ precision of 30 ppt for OCS and 3 ppb for CO at 0.5 Hz time resolution. For CO2, high absorption at atmospheric mixing ratios leads to saturation effects that limit sensitivity and complicate the spectral analysis, resulting in too large uncertainties for scientific use. For H2O, absorption is too weak to be measured at mixing ratios below 100 ppm. By further reducing electrical noise and improving the treatment of the baseline in the spectral retrieval, we hope to improve precision for OCS and CO, resolve the issues inhibiting useful CO2 measurements, and lower the detection limit for H2O. The 1035 and 3331 cm−1 arrangements have only partially been characterized and are still in development. Although both setups have been flown and recorded infrared spectra during field campaigns, no data for scientific use have yet been produced due to unresolved deviations of the retrieved mixing ratios to known standards (O3) or insufficient sensitivity (NH3, HCN, C2H2, N2O). The ∼100 kg instrument with a typical in-flight power consumption of about 500 VA is dimensioned to fit into one 19 in. rack typically used for deployment inside the aircraft cabin. Its rugged design and a pressurized and temperature-stabilized compartment containing the sensitive optical and electronic hardware also allow for deployment in payload bays outside the pressurized cabin even at high altitudes of 20 km. A sample flow system with two parallel proportional solenoid valves of different size orifices allows for precise regulation of cavity pressure over the wide range of inlet port pressures encountered between the ground and maximum flight altitudes. Sample flow of the order of 1 SLM (standard litre per minute) maintained by an exhaust-side pump limits the useful time resolution to about 2.5 s (corresponding to the average cavity flush time), equivalent to 500 m distance at a typical aircraft speed of 200 m s−1.

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Takahashi, Kosaku, Hirotaka Monzen, Toshihiro Yamaoka, Koji Kusumoto, Kazuhiro Bansaku, Jyunichi Kimoto, Akira Isoe, Yasuo Hirose, Tomio Sanda et Yuji Matsuzaki. « Noise and vibration reduction technology in aircraft cabins ». Advanced Composite Materials 13, n^o 1 (janvier 2004) : 67–80. http://dx.doi.org/10.1163/1568551041408787.

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Thèses sur le sujet "Aircraft cabins Noise Measurement"

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Kestell, Colin D. « Active control of sound in a small single engine aircraft cabin with virtual error sensors ». Title page, abstract and contents only, 2000. http://web4.library.adelaide.edu.au/theses/09PH/09phk423.pdf.

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Robert, Rene Jean. « Measuring noise level reduction using an artificial noise source ». Thesis, Georgia Institute of Technology, 2015. http://hdl.handle.net/1853/54480.

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Buildings located near airports may be subjected to significant noise levels due to aircraft flyovers. Aircraft noise is particularly annoying when compared to other traffic noises due to its intermittent nature. While noise control is typically performed at the source, sound insulation programs are in place to improve the acoustic performance of a residence affected by the flyovers. Noise Level Reduction (NLR) is a common metric used in the United States to determine whether a residence qualifies for such programs. Sound insulation programs are available to houses that have an indoor Day Night Average Sound Level (DNL) greater than 45 dBA. NLR is a single-number metric used to quantify the ability for a building or building element to reduce the transmission of external sound pressure levels generated by aircraft. In addition to determining whether a residence qualifies, NLR can be used to quantify the effectiveness of the modifications performed as a result of the sound insulation program. NLR measurements with a loudspeaker offer an alternative method to those performed with aircraft flyovers, offering flexibility to the consultants that perform these measurements in the field. The purpose of this research was to better understand and improve the loudspeaker test for measuring NLR, providing a resource to the aircraft noise industry. Testing was completed on a "test house" that was constructed on campus with construction methods typical of a mixed-humid climate. The angular dependency, repeatability, and reproducibility of NLR, among other factors, were evaluated with field measurements. Significant NLR variations were observed with changes in lateral and vertical angles of incidence.

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Camponogara, Ândrei. « Measurement and characterization of aircraft PLC channels ». Universidade Federal de Juiz de Fora (UFJF), 2016. https://repositorio.ufjf.br/jspui/handle/ufjf/5516.

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Esta dissertação tem como objetivo discutir a caracterização da rede de energia elétrica que alimenta os equipamentos de instrumentação de uma aeronave de ensaios de voo. Para a caracterização desses canais, uma campanha de medição foi realizada dentro da aeronave, de forma que dois arranjos de cabos foram adotados. Um representa a topologia em árvore, típica em aeronaves, enquanto que o segundo refere-se a uma proposta, a qual tem por objetivo compensar os problemas causados pelo modo comum através da redução do efeito de multi-percurso. No intuito de auxiliar o desenvolvimento das novas gerações de tecnologia de comunicação via rede de energia elétrica (power line communication -PLC) para aeronave e levando em conta o padrão aeronáutico RTCA/DO-160G, análises dos canais PLC medidos são realizadas em termos de ganho médio do canal, raiz quadrada do atraso médio de propagação, tempo de coerência, banda de coerência e capacidade do canal. Em relação ao ruído aditivo medido, análises da densidade espectral de potência e informações estatísticas são descritas. Além disso, distribuições de probabilidade são consideradas para modelá-lo e parâmetros do ruído impulsivo são discutidos. Em seguida, análises da impedância de acesso mostram importantes características dos cabos de ener-gia elétrica utilizados para alimentar os equipamentos de instrumentação da aeronave de ensaios de voo. Por fim, comparações entre os canais PLC medidos em residências Brasilei-ras mostram que a tecnologia PLC disponível no mercado (desenvolvida para residências) é útil para aplicações em aeronave.
This dissertation aims to discuss the characterization of the flight test aircraft power line channels related to the 28 Vdc electric power grids designed to supply energy to the in-strumentation equipments. For characterizing these channels, a measurement campaign was carried out aboard an aircraft and two data communication configurations of power lines were taken into account. While one represents a typical aircraft tree-shape topology of cable bundles, the second one is a proposal aiming at compensating the common-mode problems by reducing the multipath effects. In the light of aeronautic standard RTCA/DO-160G, analyses of measured power line communication (PLC) channels in terms of average channel gain, root mean square - delay spread, coherence time, coher-ence bandwidth, and channel capacity gives some directions to design novel generations of PLC technology for aircraft applications. Regarding the measured additive noises, anal-yses based on power spectral density and evaluated statistic information are addressed. Moreover, symmetric statistical distributions are considered to model the measured addi-tive noise. In addition, parameters of impulsive presence in the measured additive noise are discussed, and analysis of the access impedance shows some important characteristics of typical power lines used to supply energy to instrumentation equipments in a flight test aircraft. Finally, a comparison with the Brazilian in-home PLC channels shows that the PLC technology on-the-shelf (designed for in-home PLC) is also useful for aircraft applications.

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Thomas, Ashwin Paul. « Simulated and laboratory models of aircraft sound transmission ». Thesis, Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/52319.

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With increased exposure to transportation noise, there have been continued efforts to help insulate homes from aircraft noise. Current aircraft noise guidelines are based primarily on outdoor sound levels. As people spend the majority of their time indoors, however, human perception is evidently more related to indoor sound levels. Investigations are being made to provide further insight into how typical residential constructions affect indoor response. A pilot study has built a single-room "test house", according to typical construction for mixed-humid climate regions, and has directly measured outdoor-to-indoor transmission of sound - with specific focus on continuous commercial aircraft signatures. The results of this study are being used to validate and improve modelling software that simulates a wide range of construction types and configurations for other US climate regions. The improved models will allow for increased flexibility in simulating the impacts of acoustic and energy retrofits. Overall, the project intends to improve the ability to predict acoustic performance for typical US construction types as well as for any possible design alterations for sound insulation.

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Issarayangyun, Tharit Civil &amp Environmental Engineering Faculty of Engineering UNSW. « Aircraft noise and public health : acoustical measurement and social survey around Sydney (Kingsford Smith) Airport ». Awarded by:University of New South Wales. Civil and Environmental Engineering, 2005. http://handle.unsw.edu.au/1959.4/22394.

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The development of major commercial airports promotes the air transport industry and generates positive economic benefits to the airport and to its host economy. However, external costs are associated with these benefits. Any increase in aircraft movement causes negative environmental impacts, especially noise pollution. Governments have reduced aircraft noise levels at their sources, or introduced aircraft noise management strategies (ANMS); however the problems have never been satisfactorily resolved. This research aims at developing a better understanding of the impacts of aircraft noise on community health and well-being by exploring two core research questions: (1) ???Is health related quality of life worse in communities chronically exposed to aircraft noise than in communities not exposed????; and (2) ???Does long-term aircraft noise exposure associate with adult high blood pressure level via noise stress as a mediating factor????. The Sydney (Kingsford Smith) Airport has been selected as a case study. The health survey instruments have been developed and piloted, and then translated from English into Greek and Arabic. A postal self-administrative health survey (with follow-up letters) has been implemented in the areas surrounding Sydney Airport (called ???aircraft noise exposure group???) and in the matched control group. The total sample size was 1,500 with 47% response rate. This thesis has developed a ???new??? noise index (named Noise Gap Index, NGI) to describe and assess aircraft noise in such a way that is easily understood by the layperson. Factorial analysis of covariance revealed that ???Health related quality of life, in term of physical functioning, general health, vitality, and mental health, of community chronically exposed to high aircraft noise level were worse than the matched control area???. Binary logistic regression analysis found that ???Subjects (aged 15 ??? 87) who have been chronically exposed to high aircraft noise level have the odds of 2.61 of having chronic noise stress. In addition person who have chronic noise stress have the odds of 2.74 of having hypertension compared with those without chronic noise stress???. Finally, the robust hypotheses of effects of aircraft noise on community health and well-being for future experimental study were proposed.

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Thabet, Rihab El Houda. « Détection de défauts des systèmes non linéaires à incertitudes bornées continus ». Thesis, Bordeaux, 2014. http://www.theses.fr/2014BORD0283/document.

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La surveillance des systèmes industriels et/ou embarqués constitue une préoccupation majeure en raison de l’accroissement de leur complexité et des exigences sur le respect des profilsde mission. La détection d’anomalies tient une place centrale dans ce contexte. Fondamentalement,les procédures de détection à base de modèles consistent à comparer le fonctionnement réel dusystème avec un fonctionnement de référence établi à l’aide d’un modèle sans défaut. Cependant,les systèmes à surveiller présentent souvent des dynamiques non linéaires et difficiles à caractériserde manière exacte. L’approche retenue dans cette thèse consiste à englober leur influencepar des incertitudes bornées. La propagation de ces incertitudes permet l’évaluation de seuils dedécision visant à assurer le meilleur compromis possible entre sensibilité aux défauts et robustesseaux perturbations tout en préservant une complexité algorithmique raisonnable. Pour cela, unepart importante du travail porte sur l’extension des classes de modèles dynamiques à incertitudesbornées pour lesquels des observateurs intervalles peuvent être obtenus avec les preuves d’inclusionet de stabilité associées. En s’appuyant sur des changements de coordonnées variant dans letemps, des dynamiques LTI, LPV et LTV sont considérées graduellement pour déboucher sur desclasses de dynamiques Non Linéaires à Incertitudes Bornées continues (NL-IB). Une transformationdes modèles NL-IB en modèles LPV-IB a été utilisée. Une première étude sur les non-linéaritésd’une dynamique de vol longitudinal est présentée. Un axe de travail complémentaire porte surune caractérisation explicite de la variabilité (comportement aléatoire) du bruit de mesure dansun contexte à erreurs bornées. En combinant cette approche à base de données avec celle à basede modèle utilisant un prédicteur intervalle, une méthode prometteuse permettant la détection dedéfauts relatifs à la position d’une surface de contrôle d’un avion est proposée. Une étude portenotamment sur la détection du blocage et de l’embarquement d’une gouverne de profondeur
The monitoring of industrial and/or embedded systems is a major concern accordingto their increasing complexity and requirements to respect the mission profiles. Detection of anomaliesplays a key role in this context. Fundamentally, model-based detection procedures consist incomparing the true operation of the system with a reference established using a fault-free model.However, the monitored systems often feature nonlinear dynamics which are difficult to be exactlycharacterized. The approach considered in this thesis is to enclose their influence through boundeduncertainties. The propagation of these uncertainties allows the evaluation of thresholds aimingat ensuring a good trade-off between sensitivity to faults and robustness with respect to disturbanceswhile maintaining a reasonable computational complexity. To that purpose, an importantpart of the work adresses the extension of classes of dynamic models with bounded uncertaintiesso that interval observers can be obtained with the related inclusion and stability proofs. Based ona time-varying change of coordinates, LTI, LPV and LTV dynamics are gradually considered tofinally deal with some classes classes of nonlinear continuous dynamics with bounded uncertainties.A transformation of such nonlinear models into LPV models with bounded uncertainties has beenused. A first study on nonlinearities involved in longitudinal flight dynamics is presented. A complementarywork deals with an explicit characterization of measurement noise variability (randombehavior of noise within measurement) in a bounded error context. Combining this data-drivenapproach with a model-driven one using an interval predictor, a promising method for the detectionof faults related to the position of aircraft control surfaces is proposed. In this context, specialattention has been paid to the detection of runaway and jamming of an elevator

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Kestell, Colin D. (Colin David). « Active control of sound in a small single engine aircraft cabin with virtual error sensors ». 2000. http://thesis.library.adelaide.edu.au/public/adt-SUA20010216.164243/index.html.

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Bibliography: p. 199-207. Electronic publication; full text available in PDF format; abstract in HTML format. Describes the basis of a theoretical and experimental project, directed at the design and evaluation of a practical active noise control system suitable for a single light engine aircraft. The performance of virtual sensors were evaluated both analytically and experimentally in progressively more complex environments to identify their capabilities and limitations. Electronic reproduction.[Australia] :Australian Digital Theses Program,2001.

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Lee, Tsuan-Hsi, et 李纘錫. « Noise Measurement and Analysis of ship cabins ». Thesis, 2016. http://ndltd.ncl.edu.tw/handle/50828305491709483889.

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碩士
國立高雄海洋科技大學
輪機工程研究所
104
Since the living standard of human race is improving, the ship owner has more and more strict requirements on vibration and noise problem of the ship. Firstly, this thesis will carry out the measurement and analysis of the ship noise. Then, the noise source will be identified. Finally, recommendations for noise improvement of ship will be given. Keywords: ship, noise, noise control

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Rocha, Joana Luiz Torres da. « Coupled structural-acoustic analytical models for the prediction of turbulent boundary-layer-induced noise in aircraft cabins ». Thesis, 2010. http://hdl.handle.net/1828/6834.

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Significant interior noise and vibrations in aircraft cabins are generated by the turbulent flow over the fuselage. The turbulent boundary layer (TBL) excitation is the most important noise source for jet powered aircraft during cruise flight. Reduced levels of interior noise are desirable both for comfort and health reasons. However, to efficiently design noise control systems, and to design new and optimized structures that are more efficient in the noise reduction, a clearer understanding of the sound radiation and transmission mechanisms is crucial. This task is far from being straightforward, mainly due to the complexity of the system consisted by the aircraft fuselage, and all the sound transmission mechanisms involved in a such complex environment. The present work aims to give a contribution for the understanding of these mechanisms. For that, a coupled aero-vibro-acoustic analytical model for the prediction of the TBL-induced noise and vibration in aircraft is developed. Closed form analytical expressions are obtained to predict the structural vibration levels, noise radiated from the structure and interior sound pressure levels.
Graduate

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Issarayangyun, Tharit. « Aircraft noise and public health : acoustical measurement and social survey around Sydney, Kingsford Smith Airport / ». 2005. http://www.library.unsw.edu.au/~thesis/adt-NUN/public/adt-NUN20050830.232517/index.html.

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Livres sur le sujet "Aircraft cabins Noise Measurement"

1

Cole, J. E. Structureborne noise measurements on a small twin-engine aircraft. Hampton, Va : Langley Research Center, 1988.

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2

Heller, H. Aircraft exterior noise measurement and analysis techniques. Neuilly sur Seine : Agard, 1991.

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3

Heller, H. Aircraft exterior noise measurement and analysis techniques. Neuilly-sur-Seine : AGARD, 1991.

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4

McCurdy, David A. Annoyance caused by aircraft en route noise. Hampton, Va : Langley Research Center, 1992.

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Simpson, K. C. Vancouver International Airport aircraft noise monitoring system selection of remote monitoring sites. Vancouver, B.C : Transport Canada, 1985.

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Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 Wind Tunnel and extrapolated to far field. Moffett Field, Calif : Ames Research Center, 1991.

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Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 wind tunnel and extrapolated to far field. [Washington, DC] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 wind tunnel and extrapolated to far field. [Washington, DC] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Brase, L. O. Exhaust environment measurements of a turbofan engine equipped with an afterburner and 2D nozzle. [Washington, D.C.] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Block, P. J. W. Directory and trends of noise generated by a propeller in a wake. Hampton, Va : Langley Research Center, 1986.

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Plus de sources

Chapitres de livres sur le sujet "Aircraft cabins Noise Measurement"

1

Fidell, Sanford, et Vincent Mestre. « Aircraft Noise Measurement and Modeling ». Dans A Guide To U.S. Aircraft Noise Regulatory Policy, 59–74. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-39908-5_4.

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2

Taylor, J. O. « The Use of Barkhausen Noise for the Measurement of Residual Stresses in Aircraft Parts ». Dans Review of Progress in Quantitative Nondestructive Evaluation, 1715–22. Boston, MA : Springer US, 1997. http://dx.doi.org/10.1007/978-1-4615-5947-4_224.

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3

Rodríguez Timaná, Luis Carlos, Diego Fernando Saavedra Lozano, María Fernanda Díaz Velásquez et Javier Ferney Castillo García. « Technical Feasibility for the Mobile Measurement of Noise Pollution by Remotely Piloted Aircraft System ». Dans Communications in Computer and Information Science, 219–30. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-42531-9_18.

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Actes de conférences sur le sujet "Aircraft cabins Noise Measurement"

1

Greßkowski, Julian, Sten Böhme et Delf Sachau. « Global Active Noise Control in Aircraft Cabins ». Dans 15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference). Reston, Virigina : American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-3242.

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da Rocha, Joana, Afzal Suleman et Fernando Lau. « Prediction of Turbulent Flow-Induced Noise in Aircraft Cabins ». Dans ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-39231.

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Flow-induced noise in aircraft cabins can be predicted through analytical models or numerical methods. However, the analytical methods existent nowadays were obtained for simple structures and cabins, in which, usually, a single panel is excited by the turbulent flow, and coupled with an acoustic enclosure. This paper discusses the development of analytical models for the prediction of aircraft cabin noise induced by the external turbulent boundary layer (TBL). The coupled structural-acoustic analytical model is developed using the contribution of both structural and acoustic natural modes. While, in previous works, only the contribution of an individual panel to the cabin interior noise was considered, here, the simultaneous contribution of multiple flow-excited panels is also analyzed. The analytical models were developed for rectangular and cylindrical cabins. The mathematical models were successfully validated through the good agreement with several independent experimental studies. Analytical predictions are presented for the interior sound pressure level (SPL) at different locations inside the cabins. It is shown that identical panels located at different positions have dissimilar contributions to the cabin interior noise, showing that the position of the vibrating panel is an important variable for the accurate prediction of cabin interior noise. Additionally, the results show that the number of vibrating panels significantly affects the interior noise levels. It is shown that the average SPL, over the cabin volume, increases with the number of vibrating panels. The space-averaged SPL is usually accepted to provide the necessary information for the noise prediction. However, in some real life applications, the local sound pressure may be desirable. To overcome this point, the model is also able to predict local SPL values, at specific locations in the cabin, which are also affected by number of vibrating panels, and often differ from the average SPL values. The developed analytical model can be used to study a wide range of different systems involving a cabin coupled with vibrating panels, excited by the TBL. The properties of the external flow, acoustic cabin, and panels, as well as the number of vibrating panels, can be easily changed to represent different systems. These abilities of the model make it a solid basis for future investigations involving the implementation of noise reduction techniques and multidisciplinary design optimization analyzes.

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3

Bonillo, Alejandro. « Optimization of structural countermeasures for noise attenuation in aircraft cabins ». Dans 19th AIAA/CEAS Aeroacoustics Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-2230.

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Dolmans, Jeroen, et Howard Patrick. « The application of active noise control in single engine general aviation aircraft cabins ». Dans 4th AIAA/CEAS Aeroacoustics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2235.

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Grewal, A., D. Zimcik, L. Hurtubise, B. Leigh, A. Grewal, D. Zimcik, L. Hurtubise et B. Leigh. « Active noise and vibration control of turboprop aircraft cabins using multiple piezoelectric actuators ». Dans 3rd AIAA/CEAS Aeroacoustics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1638.

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6

Turgut, Enis, Mustafa Cavcar, Ozan D. Yay, Elif Yilmaz, Mehmet Ucarsu, Oznur Usanmaz, Tuncay Dogeroglu, Kadir Armutlu et Richard Miake-Lye. « Test Cell Emission Measurement of Commercial Aircraft Engine : CFM56-7B26 ». Dans AIAA/3AF Aircraft Noise and Emissions Reduction Symposium. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3167.

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Lee, Sang Soo. « Phased-Array Measurement of Modern Regional Aircraft Turbofan Engine Noise ». Dans 12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference). Reston, Virigina : American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-2653.

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Ananthanarayanan, S., A. Magleby et C. Furse. « Measurement and modeling of noise and interference in aircraft system ». Dans 2010 IEEE International Symposium Antennas and Propagation and CNC-USNC/URSI Radio Science Meeting. IEEE, 2010. http://dx.doi.org/10.1109/aps.2010.5561054.

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SMITH, M. « Aircraft noise measurement - Alternatives to the standard 1-2 metresmicrophone height ». Dans 10th Aeroacoustics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1960.

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Chappuis, Johanna, Besluau François et Polin Matthieu. « Air conditioning system noise measurement and characterization for aircraft ground operations ». Dans 17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference). Reston, Virigina : American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2934.

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Rapports d'organisations sur le sujet "Aircraft cabins Noise Measurement"

1

Fidell, Sanford, Richard Howe, Barbara Tabachnick, Karl Pearsons, Laura Silvati, Matthew Sneddon et Elizabeth Fletcher. Field Studies of Habituation to Change in Nighttime Aircraft Noise and of Sleep Motility Measurement Methods. Fort Belvoir, VA : Defense Technical Information Center, mars 1998. http://dx.doi.org/10.21236/ada388876.

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